Airworthiness Directives; The Boeing Company Airplanes, 78515-78518 [2022-27803]
Download as PDF
<![CDATA[
78515
Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations
TABLE 1 TO PARAGRAPH (c)—AFFECTED HPT STAGE 2 DISKS, FORWARD SEALS, AND STAGES 6–10 COMPRESSOR
ROTOR SPOOLS
Part name
P/N
HPT stage 2 disk .....................................................................................................................................................
2300M84P02
Forward seal ............................................................................................................................................................
2417M60P02
or
2759M04P01
Stages 6–10 compressor rotor spool ......................................................................................................................
2357M30G02
or
2340M36G01
2439M35G01
or
2610M90G01
Stages 6–10 compressor rotor spool ......................................................................................................................
Stages 6–10 compressor rotor spool ......................................................................................................................
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer
investigation that revealed that certain HPT
stage 2 disks, forward seals, and stages 6–10
compressor rotor spools were manufactured
from powder metal material suspected to
contain iron inclusion. The FAA is issuing
this AD to prevent fracture and potential
uncontained failure of certain HPT stage 2
disks, forward seals, and stages 6–10
compressor rotor spools. The unsafe
condition, if not addressed, could result in
uncontained debris release, damage to the
engine, and damage to the aircraft.
lotter on DSK11XQN23PROD with RULES1
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Before exceeding 600 flight cycles after
the effective date of this AD, remove the
affected HPT stage 2 disk, forward seal, and
stages 6–10 compressor rotor spool from
service and replace with a part eligible for
installation.
(2) For affected engines not in service,
before further flight, remove the affected HPT
stage 2 disk, forward seal, and stages 6–10
compressor rotor spool and replace with a
part eligible for installation.
(h) Definitions
(1) For the purpose of this AD, a ‘‘part
eligible for installation’’ is any HPT stage 2
disk, forward seal, or stages 6–10 compressor
VerDate Sep<11>2014
16:02 Dec 21, 2022
Jkt 259001
rotor spool with a P/N and S/N not identified
in Table 1 to paragraph (c) of this AD.
(2) For the purpose of this AD, ‘‘engines
not in service’’ are engines that are in longterm or short-term storage as of the effective
date of this AD.
(i) Installation Prohibition
After the effective date of this AD, do not
install an HPT stage 2 disk, forward seal, or
stages 6–10 compressor rotor spool with a P/
N and S/N identified in Table 1 to paragraph
(c) of this AD onto any engine.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO Branch, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to the attention of the person
identified in paragraph (k) of this AD and
email to: ANE-AD-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(k) Related Information
For more information about this AD,
contact Alexei Marqueen, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7178; email: Alexei.T.Marqueen@
faa.gov.
(l) Material Incorporated by Reference
None.
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
2439M35G02
S/N
TMT4AF08
TMT4AF10
TMT4AF11
TMT4AF12
VOLF1931
VOLF1933
VOLF1942
VOLF1977
VOLF1993
VOLF2014
GWN0R86N
GWN0RCKT
GWN0R62G
GWN0R86J
GWN0R5EK
GWN0R6EH
GWN0R7K1
GWN0R89A
GWN0RA89
GWN0R6K9
GWN0R7G9
GWN0R7K4
GWN0R752
GWN0R98P
Issued on December 2, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–27835 Filed 12–21–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–1054; Project
Identifier AD–2022–00278–T; Amendment
39–22255; AD 2022–24–15]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2017–18–
05, which applied to all The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
series airplanes. AD 2017–18–05
required repetitive replacement or
inspection of certain fuse pins, and
applicable on-condition actions. This
AD was prompted by a report of damage
found at the lower trailing edge panels
SUMMARY:
E:\FR\FM\22DER1.SGM
22DER1
78516
Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations
of the left wing and a broken fuse pin
of the landing gear beam end fitting.
This AD was further prompted by the
need for new inspections for cracking of
the fuse pin, and the determination that
additional airplanes are subject to the
unsafe condition. This AD continues to
require the actions in AD 2017–18–05
and also requires repetitive replacement
of certain fuse pins, repetitive
inspections for cracking of the fuse pin,
and applicable on-condition actions.
This AD also revises the applicability by
adding airplanes. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective January 26,
2023.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 26, 2023.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2022–1054; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, any comments
received, and other information. The
address for Docket Operations is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
Material Incorporated by Reference:
• For service information identified
in this final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110–SK57,
Seal Beach, CA 90740–5600; telephone
562–797–1717; website
myboeingfleet.com.
• You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available at
regulations.gov under Docket No. FAA–
2022–1054.
FOR FURTHER INFORMATION CONTACT:
Stefanie Roesli, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone: 206–231–
3964; email: Stefanie.N.Roesli@faa.gov.
Discussion of Final Airworthiness
Directive
SUPPLEMENTARY INFORMATION:
The FAA received a comment from
Air Line Pilots Association,
International, who supported the NPRM
without change.
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017–18–05,
Amendment 39–19014 (82 FR 41331,
August 31, 2017) (AD 2017–18–05). AD
2017–18–05 applied to all Boeing Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747–400, 747–400D, 747–400F,
747SR, and 747SP airplanes. The NPRM
published in the Federal Register on
September 19, 2022 (87 FR 57155). The
NPRM was prompted by a report of
damage at the lower trailing edge panels
of the left wing and a broken fuse pin
of the landing gear beam end fitting. The
NPRM was further prompted by the
need for new ultrasonic testing (UT)
inspections for cracking of the fuse pin,
and the determination that additional
airplanes are subject to the unsafe
condition. In the NPRM, the FAA
proposed to continue to require
repetitive replacement, or repetitive
magnetic particle or surface high
frequency eddy current (HFEC)
inspections, of certain fuse pins, and
applicable on-condition actions. The
NPRM also proposed the option for
repetitive replacement of certain
corrosion-resistant (stainless) steel
(CRES) and steel alloy fuse pins at the
wing landing gear beam end fitting; and
repetitive magnetic particle inspections,
or repetitive HFEC and UT inspections,
for cracking of the fuse pin, and
applicable on-condition actions. The
NPRM also proposed to revise the
applicability by adding Model 747–8F
and 747–8 series airplanes.
The FAA is issuing this AD to address
cracking in the fuse pin of the wing
landing gear beam end fitting. A broken
fuse pin will not support the wing
landing gear beam, causing damage to
the surrounding structure, including
flight control cables and hydraulic
systems, which could result in loss of
controllability of the airplane.
Comments
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, this AD is adopted as proposed
in the NPRM. None of the changes will
increase the economic burden on any
operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Service Bulletin 747–57A2360, Revision
1, dated February 9, 2022. This service
information specifies procedures for,
depending on airplane configuration,
the optional repetitive replacement of
certain steel alloy fuse pins or CRES
fuse pins with new or serviceable fuse
pins at the wing landing gear beam end
fitting; and repetitive magnetic particle
inspections, or repetitive surface HFEC
and UT inspections, for cracking and
corrosion of the fuse pin of the wing
landing gear beam end fitting, and
applicable on-condition actions. Oncondition actions include replacement
with steel alloy or CRES fuse pins; and
magnetic particle, surface HFEC, and
UT testing inspections for cracks; and
replacement of cracked fuse pins. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in ADDRESSES.
Costs of Compliance
The FAA estimates that this AD
affects 207 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS
Action
lotter on DSK11XQN23PROD with RULES1
replacement 1
Fuse pin
(retained actions from AD 2017–18–05).
Magnetic particle inspection 1 (retained
actions from AD 2017–18–05).
Surface inspection 1 (retained actions
from AD 2017–18–05).
VerDate Sep<11>2014
16:02 Dec 21, 2022
Labor cost
Parts cost
Up to 46 work–hours × $85 per
hour = Up to $3,910 per replacement cycle.
Up to 48 work-hours × $85 per
hour = Up to $4,080 per inspection cycle.
Up to 10 work-hours × $85 per
hour = Up to $850 per inspection cycle.
Up to $15,150 ....
Up to $19,060 per replacement
cycle.
Up to $3,945,420 per replacement cycle.
$0 .......................
Up to $4,080 per inspection
cycle.
Up to $844,560 per inspection
cycle.
$0 .......................
Up to $850 per inspection cycle
Up to $175,950 per inspection
cycle.
Jkt 259001
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Cost per product
E:\FR\FM\22DER1.SGM
22DER1
Cost on U.S. operators
Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations
78517
ESTIMATED COSTS—Continued
Action
CRES fuse pin replacement 1 (new action).
Steel alloy fuse pin replacement 1 (new
action).
Surface HFEC and UT inspections1
(new action).
1 Operators
Labor cost
Parts cost
Up to 46 work-hours × $85 per
hour = Up to $3,910 per replacement cycle.
Up to 46 work-hours × $85 per
hour = Up to $3,910 per replacement cycle.
Up to 11 work-hours × $85 per
hour = Up to $935 per inspection cycle.
$9,007 ................
Up to $12,917 per replacement
cycle.
Cost per product
Up to $2,673,819 per replacement cycle.
Cost on U.S. operators
$9,693 ................
Up to $13,603 per replacement
cycle.
Up to $2,815,821 per replacement cycle.
$0 .......................
Up to $935 per inspection cycle
Up to $193,545 per inspection
cycle.
may choose which action they want to use.
The FAA estimates the following
costs to do any necessary replacements
and inspections that would be required
based on the results of the required
inspections. The FAA has no way of
determining the number of aircraft that
might need these replacements and
inspections:
ON-CONDITION COSTS
Action
Labor cost
CRES fuse pin replacement .........................................
Steel alloy fuse pin replacement ..................................
Magnetic particle inspection .........................................
Surface HFEC and UT inspections ..............................
Authority for This Rulemaking
lotter on DSK11XQN23PROD with RULES1
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
$85
$85
$85
$85
per
per
per
per
hour
hour
hour
hour
=
=
=
=
$3,910 ......................
$3,910 ......................
$4,080 ......................
$935 .........................
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
■
■
Jkt 259001
×
×
×
×
List of Subjects in 14 CFR Part 39
§ 39.13
16:58 Dec 21, 2022
work-hours
work-hours
work-hours
work-hours
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Regulatory Findings
VerDate Sep<11>2014
46
46
48
11
Parts cost
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2017–18–05; Amendment 39–
19014 (82 FR 41331, August 31, 2017);
and
■ b. Adding the following new AD:
Cost per
product
$9,007
9,693
0
0
$12,917
13,603
4,080
35
(b) Affected ADs
This AD replaces AD 2017–18–05;
Amendment 39–19014 (82 FR 41331, August
31, 2017) (AD 2017–18–05).
(c) Applicability
This AD applies to all The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, 747SP, 747–8F, and 747–8 series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of
damage found at the lower trailing edge
panels of the left wing and a broken fuse pin
of the landing gear beam end fitting, and the
determination that repetitive ultrasonic
testing inspections of the fuse pin for
cracking and optional repetitive replacement
of certain corrosion-resistant (stainless) steel
(CRES) and steel alloy fuse pins are necessary
to address the unsafe condition. The FAA is
issuing this AD to detect and correct cracking
in the fuse pin of the wing landing gear beam
end fitting. A broken fuse pin will not
support the wing landing gear beam, causing
damage to the surrounding structure,
including flight control cables and hydraulic
systems, which could result in loss of
controllability of the airplane.
2022–24–15 The Boeing Company:
Amendment 39–22255; Docket No.
FAA–2022–1054; Project Identifier AD–
2022–00278–T.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(a) Effective Date
This airworthiness directive (AD) is
effective January 26, 2023.
(g) Required Actions
Except as specified by paragraph (h) of this
AD: At the applicable times specified in
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
E:\FR\FM\22DER1.SGM
22DER1
78518
Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–57A2360,
Revision 1, dated February 9, 2022, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2360, Revision 1, dated February 9,
2022.
lotter on DSK11XQN23PROD with RULES1
(h) Exceptions to Service Information
Specifications
(1) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Service Bulletin 747–
57A2360, Revision 1, dated February 9, 2022,
use the phrase ‘‘the original issue date of this
service bulletin,’’ this AD requires using the
date of October 5, 2017 (the effective date of
AD 2017–18–05).
(2) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Service Bulletin 747–
57A2360, Revision 1, dated February 9, 2022,
use the phrase ‘‘the Revision 1 date of this
service bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (j) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(4) Except as specified by paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (ii) of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
VerDate Sep<11>2014
16:02 Dec 21, 2022
Jkt 259001
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
For more information about this AD,
contact Stefanie Roesli, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone: 206–231–3964; email:
Stefanie.N.Roesli@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747–
57A2360, Revision 1, dated February 9, 2022.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; website
myboeingfleet.com.
(4) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
St., Des Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fr.inspection@nara.gov, or go to
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on November 18, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–27803 Filed 12–21–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–1570; Project
Identifier MCAI–2022–01269–T; Amendment
39–22268; AD 2022–25–12]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Airbus SAS Model A310 series
airplanes. This AD was prompted by a
determination that new or more
restrictive maintenance requirements
and airworthiness limitations are
necessary. This AD requires revising the
existing maintenance or inspection
program, as applicable, to incorporate
new or more restrictive airworthiness
limitations, as specified in a European
Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD becomes effective
January 6, 2023.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 6, 2023.
The FAA must receive comments on
this AD by February 6, 2023.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
regulations.gov. Follow the instructions
for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2022–1570; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The street address for
Docket Operations is listed above.
Material Incorporated by Reference:
• For material incorporated by
reference in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
website easa.europa.eu. You may find
this material on the EASA website at
ad.easa.europa.eu.
• You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA,
call (206) 231–3195. It is also available
at regulations.gov under Docket No.
FAA–2022–1570.
E:\FR\FM\22DER1.SGM
22DER1
]]>Agencies
[Federal Register Volume 87, Number 245 (Thursday, December 22, 2022)]
[Rules and Regulations]
[Pages 78515-78518]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-27803]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-1054; Project Identifier AD-2022-00278-T;
Amendment 39-22255; AD 2022-24-15]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2017-18-
05, which applied to all The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SR, and 747SP series airplanes. AD 2017-18-05 required
repetitive replacement or inspection of certain fuse pins, and
applicable on-condition actions. This AD was prompted by a report of
damage found at the lower trailing edge panels
[[Page 78516]]
of the left wing and a broken fuse pin of the landing gear beam end
fitting. This AD was further prompted by the need for new inspections
for cracking of the fuse pin, and the determination that additional
airplanes are subject to the unsafe condition. This AD continues to
require the actions in AD 2017-18-05 and also requires repetitive
replacement of certain fuse pins, repetitive inspections for cracking
of the fuse pin, and applicable on-condition actions. This AD also
revises the applicability by adding airplanes. The FAA is issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective January 26, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 26,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1054; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; website myboeingfleet.com.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available at
regulations.gov under Docket No. FAA-2022-1054.
FOR FURTHER INFORMATION CONTACT: Stefanie Roesli, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone: 206-231-3964; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2017-18-05, Amendment 39-19014 (82 FR
41331, August 31, 2017) (AD 2017-18-05). AD 2017-18-05 applied to all
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP airplanes.
The NPRM published in the Federal Register on September 19, 2022 (87 FR
57155). The NPRM was prompted by a report of damage at the lower
trailing edge panels of the left wing and a broken fuse pin of the
landing gear beam end fitting. The NPRM was further prompted by the
need for new ultrasonic testing (UT) inspections for cracking of the
fuse pin, and the determination that additional airplanes are subject
to the unsafe condition. In the NPRM, the FAA proposed to continue to
require repetitive replacement, or repetitive magnetic particle or
surface high frequency eddy current (HFEC) inspections, of certain fuse
pins, and applicable on-condition actions. The NPRM also proposed the
option for repetitive replacement of certain corrosion-resistant
(stainless) steel (CRES) and steel alloy fuse pins at the wing landing
gear beam end fitting; and repetitive magnetic particle inspections, or
repetitive HFEC and UT inspections, for cracking of the fuse pin, and
applicable on-condition actions. The NPRM also proposed to revise the
applicability by adding Model 747-8F and 747-8 series airplanes.
The FAA is issuing this AD to address cracking in the fuse pin of
the wing landing gear beam end fitting. A broken fuse pin will not
support the wing landing gear beam, causing damage to the surrounding
structure, including flight control cables and hydraulic systems, which
could result in loss of controllability of the airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from Air Line Pilots Association,
International, who supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM. None of the changes will
increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Service Bulletin 747-57A2360,
Revision 1, dated February 9, 2022. This service information specifies
procedures for, depending on airplane configuration, the optional
repetitive replacement of certain steel alloy fuse pins or CRES fuse
pins with new or serviceable fuse pins at the wing landing gear beam
end fitting; and repetitive magnetic particle inspections, or
repetitive surface HFEC and UT inspections, for cracking and corrosion
of the fuse pin of the wing landing gear beam end fitting, and
applicable on-condition actions. On-condition actions include
replacement with steel alloy or CRES fuse pins; and magnetic particle,
surface HFEC, and UT testing inspections for cracks; and replacement of
cracked fuse pins. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in ADDRESSES.
Costs of Compliance
The FAA estimates that this AD affects 207 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement \1\ Up to 46 work- Up to $15,150........ Up to $19,060 per Up to $3,945,420
(retained actions from AD 2017- hours x $85 per replacement per replacement
18-05). hour = Up to cycle. cycle.
$3,910 per
replacement cycle.
Magnetic particle inspection Up to 48 $0................... Up to $4,080 per Up to $844,560
\1\ (retained actions from AD work[dash]hours x inspection cycle. per inspection
2017-18-05). $85 per hour = Up cycle.
to $4,080 per
inspection cycle.
Surface inspection \1\ Up to 10 $0................... Up to $850 per Up to $175,950
(retained actions from AD 2017- work[dash]hours x inspection cycle. per inspection
18-05). $85 per hour = Up cycle.
to $850 per
inspection cycle.
[[Page 78517]]
CRES fuse pin replacement \1\ Up to 46 $9,007............... Up to $12,917 per Up to $2,673,819
(new action). work[dash]hours x replacement per replacement
$85 per hour = Up cycle. cycle.
to $3,910 per
replacement cycle.
Steel alloy fuse pin Up to 46 $9,693............... Up to $13,603 per Up to $2,815,821
replacement \1\ (new action). work[dash]hours x replacement per replacement
$85 per hour = Up cycle. cycle.
to $3,910 per
replacement cycle.
Surface HFEC and UT Up to 11 $0................... Up to $935 per Up to $193,545
inspections\1\ (new action). work[dash]hours x inspection cycle. per inspection
$85 per hour = Up cycle.
to $935 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
\1\ Operators may choose which action they want to use.
The FAA estimates the following costs to do any necessary
replacements and inspections that would be required based on the
results of the required inspections. The FAA has no way of determining
the number of aircraft that might need these replacements and
inspections:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
CRES fuse pin replacement..................... 46 work-hours x $85 per hour = $9,007 $12,917
$3,910.
Steel alloy fuse pin replacement.............. 46 work-hours x $85 per hour = 9,693 13,603
$3,910.
Magnetic particle inspection.................. 48 work-hours x $85 per hour = 0 4,080
$4,080.
Surface HFEC and UT inspections............... 11 work-hours x $85 per hour = 0 35
$935.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-18-05; Amendment 39-19014
(82 FR 41331, August 31, 2017); and
0
b. Adding the following new AD:
2022-24-15 The Boeing Company: Amendment 39-22255; Docket No. FAA-
2022-1054; Project Identifier AD-2022-00278-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 26, 2023.
(b) Affected ADs
This AD replaces AD 2017-18-05; Amendment 39-19014 (82 FR 41331,
August 31, 2017) (AD 2017-18-05).
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, 747SP, 747-8F, and 747-8 series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of damage found at the lower
trailing edge panels of the left wing and a broken fuse pin of the
landing gear beam end fitting, and the determination that repetitive
ultrasonic testing inspections of the fuse pin for cracking and
optional repetitive replacement of certain corrosion-resistant
(stainless) steel (CRES) and steel alloy fuse pins are necessary to
address the unsafe condition. The FAA is issuing this AD to detect
and correct cracking in the fuse pin of the wing landing gear beam
end fitting. A broken fuse pin will not support the wing landing
gear beam, causing damage to the surrounding structure, including
flight control cables and hydraulic systems, which could result in
loss of controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified by paragraph (h) of this AD: At the
applicable times specified in
[[Page 78518]]
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-57A2360, Revision 1, dated February 9, 2022, do all applicable
actions identified as ``RC'' (required for compliance) in, and in
accordance with, the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-57A2360, Revision 1, dated February 9, 2022.
(h) Exceptions to Service Information Specifications
(1) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022, use the phrase ``the
original issue date of this service bulletin,'' this AD requires
using the date of October 5, 2017 (the effective date of AD 2017-18-
05).
(2) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022, use the phrase ``the
Revision 1 date of this service bulletin,'' this AD requires using
``the effective date of this AD.''
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or responsible Flight Standards Office,
as appropriate. If sending information directly to the manager of
the certification office, send it to the attention of the person
identified in paragraph (j) of this AD. Information may be emailed
to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) Except as specified by paragraph (h) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (i)(4)(i) and (ii) of
this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(j) Related Information
For more information about this AD, contact Stefanie Roesli,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone: 206-231-3964; email:
[email protected].
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747-57A2360, Revision 1, dated
February 9, 2022.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; website myboeingfleet.com.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on November 18, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-27803 Filed 12-21-22; 8:45 am]
BILLING CODE 4910-13-P
